Specifications

SECTION II
MODEL 560 AIRPLANE AND SYSTEMS
CIRCUIT BREAKERS
Push-to-reset, pull-off type circuit breakers, with the amperage rating marked on each breaker, are
installed in panels located on both sides of the cockpit, under the side windows. Each panel incorporates
various electrical system circuit breakers with the majority of the avionics circuit breakers located in the
right circuit breaker panel. The AC BUS circuit breaker panel is located adjacent to the right circuit breaker
panel. This circuit breaker panel controls the 26 VAC and 115 VAC split bus distribution of the Number 1
and 2 static inverters. Panel configurations may vary from airplane to airplane due to differences in installed
equipment; therefore, the panels shown are typical installations.
BATTERY
The battery is a secondary source of direct current (DC) power available to supply the distribution
system prior to start, or in the event of generator failure. The three-position control switch is labeled BATT,
OFF and EMER. Placing the switch to the BATT position closes the battery and emergency relays and
powers the battery bus, emergency bus and both main DC buses. This position also enables external
power to supply the entire system. In the OFF position, battery or external power is isolated from all but the
hot battery bus.
The hot battery bus is energized any time the battery is installed or external power is connected. It
powers the emergency exit lights, tailcone light, nose baggage compartment light and an aft baggage
compartment light. A battery disconnect relay between the battery and ground is located below the battery.
During each engine start using external power, the battery disconnect relay will automatically open
interrupting battery power to the hot battery bus. The relay will close automatically at the end of the start
cycle.
The EMER (emergency) position of the battery switch will provide approximately 30 minutes operation
for selected instruments and systems. The following are powered from the emergency bus:
LH and RH N
1
Indicators Standby HSI and Standby Flight Display
Standby Pitot and Static Heaters Interior Entry Lights
Landing Gear Control and Indication DME 1 (560-0552 only)
Flap Control COMM 1
Standby Radio Control Head NAV 1
Overhead Flood Lights DG 1
Pilot’s and Copilot’s Audio Panels RMU 1
Additionally, the standby gyro’s internal battery provides at least 30 minutes lighting for the dual fan
(N
1
) tachometer/Interturbine temperature (ITT) indicators, the secondary flight display, and the standby
horizontal situation indicator (HSI).
In some cases, it may be prudent to turn OFF unneeded systems, such as lighting and pitot-static
heat, in order to conserve the airplane’s battery. Communications may be continued normally using COMM
1. The speakers will remain operational and selection of EMER COMM is not necessary.
The battery temperature monitor gage provides a continuous indication of battery temperature from 0°
to 180°F (-18° to +82°C).
Battery temperature should remain below 63°C (145°F). A battery temperature exceeding 63°C
(145°F) is annunciated by a steady illumination of the BATT O'TEMP light on the annunciator panel. A
battery temperature exceeding 71°C (160°F) is shown by a flashing annunciator light.
The battery must be serviced per the Maintenance Manual when the battery temperature exceeds
63°C (145°F).
I 56OMB-01 Configuration AA 2-37